CHAPTER FLIGHT INSTRUMENTS

Transcription

1 Table of Contents Vol CHAPTER FLIGHT INTRUMENT Page TABLE OF CONTENT Table of Contents INTRODUCTION Introduction ELECTRONIC FLIGHT INTRUMENT YTEM Electronic Flight Instrument ystem Display Reversion Display Control Comparator Function ystem Circuit Breakers AIR DATA YTEM Air Data ystem Pitot tatic ystem Air Data Air Data Reference Panels Altitude Alerts Acquisition Mode Cross ide Tracking Deviation Mode Air Data Reversion ystem Circuit Breakers RADIO ALTIMETER YTEM Radio Altimeter ystem ystem Circuit Breakers ATTITUDE AND HEADING REFERENCE YTEM Attitude and Heading Reference ystem Display Reversion Initialization and Alignment ystem Circuit Breakers TANDBY INTRUMENT AND CLOCK tandby Instruments and Clocks tandby Attitude Indicator tandby Altitude/Airspeed Indicator Integrated tandby Instrument tandby Magnetic Compass Clocks ystem Circuit Breakers

2 Table of Contents Vol HEAD -UP GUIDANCE YTEM Head--Up Guidance ystem Combiner ymbology Output to PFD s Audio Callouts Output to FDR Output to MDC Approach Monitor for Category II Operations Approach Monitor for Category III Operations ystem Test/Fault Codes HG Mode elections/indications ystem Circuit Breakers LIT OF ILLUTRATION ELECTRONIC FLIGHT INTRUMENT YTEM Figure Electronic Flight Instrument ystem (EFI) Figure EFI Interface -- Block chematic Figure Display election Figure Primary Flight Display and Multifunction Display Figure Display Control and ource elector Panels Figure Display Control ource Indications Figure Display Control ource Flags Figure EFI Abnormal Indications AIR DATA YTEM Figure Pitot tatic ystem -- General Figure Air Data ystem Figure Pitot tatic ystem Figure Air Data Reference Control Panel Figure Indicated Airspeed and Mach Indications Figure Indicated Airspeed Flag -- Primary Flight Director Figure Altitude Indications Figure Altitude Alerts Figure Minimum Descent Altitude Indications Figure Vertical peed Indication and Flag Figure ource elector -- Air Data Panel Figure Air Data Flags -- Primary Flight Display RADIO ALTIMETER YTEM Figure Radio Altimeter ystem

3 Table of Contents Vol Figure Air Data Reference Control Panel Figure Radio Altimeter Indication INERTIAL REFERENCE YTEM Figure Attitude Heading Reference ysytem/inertial Refence ystem Interface Figure Compass Control Panel/Inertial Reference ystem Mode elect Unit Figure Attitude Director Indications Figure elected Heading Readout Figure ource elector Panel Figure Attitude and Heading ource election Figure Attitude/Heading ource Failure Indications Figure Attitude/Heading ource Alignment Indications TANDBY INTRUMENT AND CLOCK Figure tandby Attitude Indicator Figure tandby Altitude/Airspeed Indicator Figure Integrated tandby Instrument Figure Integrated tandby Instrument cales Figure Integrated tandby Instrument Flags Figure tandby Magnetic Compass Figure Airplanes 7002 to 7672, Clock Display Figure Airplanes 7673 and ubsequent, Clock Display HEAD -UP GUIDANCE YTEM Figure HG ystem Figure Head--Up Guidance ystem unvisor Figure Head--Up Guidance ystem Figure HG Control Panel Figure Airplanes equipped with the (--503) HG Computer HG Control Panel Figure Head--Up Guidance ystem -- Test Mode elections Figure HG ystem -- EICA Messages Figure Primary Mode -- Radio Altitude Indications Figure HG /AFC Modes Figure HG Combiner -- General Figure Primary Mode -- Airspeed Indications Figure Primary Mode -- On Ground

4 Table of Contents Vol Figure Visual Meteorolical Conditions (VMC) Model -- Approach and Landing Figure Flight Director (F/D) Model -- Approach and Landing Figure Category I or II (AI or AII) Model Approach and Landing Figure Category IIIa (AIII) Model Approach and Landing Figure Rollout Mode Figure Primary Mode -- Attitude Indications Figure Primary Mode -- Heading Indications Figure Primary Mode -- Course Indications Figure Primary Mode -- Barometric Altitude Indications Figure Primary Mode -- Radio Altitude Indications Figure Primary Mode -- Vertical peed Indications Figure Primary Mode -- Navigation/Position Indications Figure Primary Mode -- Flight Path Indications Figure Primary Mode -- Environmental Indications Figure Unusal Attitude Display Figure Primary Mode -- Autopilot/Flight Director

5 Introduction Vol INTRODUCTION Flight instruments include the electronic flight instrument systems, standby instruments and clocks. Data for the flight instruments is provided by an air data system, radio altimeter and attitude and heading reference system (AHR). Flight instruments provide the following basic information to the flight crew: Flight instruments include the electronic flight instrument systems, standby instruments and clocks. Data for the flight instruments is provided by an air data system, radio altimeter and inertial reference system (IR). Flight instruments provide the following basic information to the flight crew: <0025> Altitude (barometric/radio) True Airspeed Airspeed (MACH/KIA) Temperature Data Airspeed Trend Airplane Attitude Vertical peed Heading Information Overspeed Warning Navigation Information. Electronic flight instruments consists of a primary flight display (PFD) and a multifunctional display (MFD) for each pilot. A standby attitude indicator and standby altitude/airspeed indicator are provided. An independent standby compass provides aircraft heading in relation to magnetic north. An electronic clock provides the time source for the aircraft avionics equipment. Electronic flight instruments consists of a primary flight display (PFD) and a multifunctional display (MFD) for each pilot. An integrated standby instrument (II) provides standby attitude, altitude and airspeed information to the flight crew. An independent standby compass provides aircraft heading in relation to magnetic north. An electronic clock provides the time source for the aircraft avionics equipment. <0083> Air data provided by a pitot-static system and a temperature probe provide the flight instruments with speed, altitude and temperature data. The radio altimeter provides an accurate measurement of height above terrain at low altitudes. The attitude and heading reference system (AHR) provides attitude, heading, position, angular rate and linear acceleration information.

6 Introduction Vol Air data provided by a pitot-static system and a temperature probe provide the flight instruments with speed, altitude and temperature data. The radio altimeter provides an accurate measurement of height above terrain at low altitudes. The inertial reference system (IR) provides attitude, heading, position, angular rate and linear acceleration information. <0025>

7 Electronic Flight Instrument ystem Vol ELECTRONIC FLIGHT INTRUMENT YTEM All basic flight information is presented to the flight crew on Electronic Flight Instrument ystem (EFI) displays. Each pilot instrument panel contains a primary flight display (PFD) and a multifunctional display (MFD). All four displays are electronically identical to permit transfer of display data. Each PFD is a digital CRT and has the primary function of pictorially showing aircraft attitude, altitude, airspeed, flight director commands and flight mode annunciations. Inputs to the PFD s are from the selected AHR and ADC s. Commands are set on the flight control panel, air data reference panel and display control panels. Each PFD is a digital CRT and has the primary function of pictorially showing aircraft attitude, altitude, airspeed, flight director commands and flight mode annunciations. Inputs to the PFD s are from the selected IR and ADC s. Commands are set on the flight control panel, air data reference panel and display control panels.<0025> The PFD s function as the following instruments: Attitude heading indicator (ADI) Horizontal situation indicator (HI) Radio magnetic indicator (RMI) Radio altimeter indicator Airspeed indicator (Mach and IA) Vertical speed indicator (VI). Each of the MFDs acts as a navigation system display and has a primary function of showing current heading (compass) and course information. The MFDs can also display moving map navigation pictorials, navigation sensor data, weather radar targets, and TCA traffic (see Chapter 18). Cross side compass information and backup navigation information can be superimposed on either display. EICA information can also be displayed on either MFD. A. Display Reversion Two display reversionary panels are installed in the flight compartment. One panel is installed on the pilot s side panel and the other panel is installed on the copilot s side panel. In the event of a PFD failure, all data normally displayed on it can be transferred to the adjacent MFD by turning the display selector knob on the respective reversionary panel to the PFD position. The MFD information cannot be transferred to the PFD. electing the EICA position will initially display the EICA status page on the respective MFD. All the other EICA pages are available for display on the MFD, through selections on the EICA control panel.

8 Electronic Flight Instrument ystem Vol tandby Airspeed/ Altitude/Attitude Indicator <0015> tandby Attitude Indicator MLG BAY OVHT DIPLAY COOL tandby Altimeter/Indicated Airspeed Indicator <0083> <0015> <0015> MLG BAY OVHT DIPLAY COOL EICA Displays Primary Flight Display (PFD) Multifunction Display (MFD) Multifunction Display (MFD) Primary Flight Display (PFD) Electronic Flight Instrument ystem (EFI) <MT> Figure

9 Electronic Flight Instrument ystem Vol PFD 1 MFD 1 MFD 2 PFD 2 CRI AP AP XFR PEED APPR HDG NAV ALT V DOWN CR2 <0040> <0040> <0025> <0025> MACH, AIRPEED, VERTICAL PEED. EFI Interface --- Block chematic <MT> Figure

10 Electronic Flight Instrument ystem Vol Used to change the pilot or copilot MFD display. PFD 1 or 2 -- MFD changes to a PFD display and PFD display goes blank. Pilot s Display Reversionary Panel Pilot s ide Panel Copilot s Display Reversionary Panel Copilot s ide Panel Display election Figure

11 Electronic Flight Instrument ystem Vol Attitude Director Indicator (ADI) Flight Director / Autopilot Mode Annunciator Airspeed Indicator (IA) Barometric Altitude <0015> Navigation ource / Course Display Horizontal ituation Indicator (HI) Vertical peed Indicator Bearing Pointer ource Primary Flight Display Pilot s and Copilot s Instrument Panels Radar Mode Line Time / Temperature / Performance Line Onside Course Display elected Heading Display Course Pointer Lateral Deviation Bar Airplane ymbol Cross--ide Course Display Bearing Pointer Lateral Deviation cale Vertical Deviation cale Bearing Pointer ource Multifunction Display - HI Mode Pilot s and Copilot s Instrument Panels Primary Flight Display and Multifunction Display <MT> Figure

12 Electronic Flight Instrument ystem Vol B. Display Control Two display control panels are installed in the flight compartment. One panel is installed on the pilot s side panel and the other panel is installed on the copilot s side panel. Each panel provides the pilot and copilot control of their respective PFD and MFD. The control selections are as follows: MFD format selection Bearing pointer selection Navigation source selection Cross side navigation data and course display. The rotary FORMAT knob can be used to select one of the following navigation formats: HI compass Navaid sector map TCA FM present position map FM plan map Weather radar. If one display control panel fails, the other panel can be used to control all four electronic flight displays. This is done by selecting the DPL CONT knob, on the ource elector Panel, to the 1 or 2 position as required.

13 Electronic Flight Instrument ystem Vol FORMAT - Outer elector Used to select MFD format. Format selections are HI compass, navaid sector, present position map (PPN), plan map, TCA and weather radar. BRG Used to select next waypoint that bearing pointer will indicate direction to. RANGE - Inner elector Used to select range displayed on MFD. Range selections are: 5, 10, 20, 40, 80, 160, 320 and 640 NM. NAV OURCE Used to select navigation source. Clockwise rotation will be FM1, VOR/LOC1, OFF, VOR/LOC2 and FM2. PUH X -IDE Used to display opposite side navigational source on MFD. RDR Used to select weather radar display. RDR / TERR Used to select weather radar display, terrain display or both. Display Control Panel Pilot s and Copilot s ide Panels <0040> TFC (TCA) Used to directly select TCA traffic display on MFD. Range selections are 5, 10, 20 and 40 NM. ource elector Panel Center Pedestal Display Control and ource elector Panels <MT> Figure

14 Electronic Flight Instrument ystem Vol <0015> Primary Flight Display Pilot s and Copilot s Instrument Panels Multifunction Display - HI Mode Pilot s and Copilot s Instrument Panels Display Control ource Indications <MT> Figure

15 Electronic Flight Instrument ystem Vol <0015> DCP, DCP 1 or DCP 2 Flag (red) Indicates that selected display control panel has failed. Primary Flight Display Pilot s and Copilot s Instrument Panels Multifunction Display - HI Mode Pilot s and Copilot s Instrument Panels Display Control ource Flags <MT> Figure

16 Electronic Flight Instrument ystem Vol EFI COMP INOP caution (amber) Indicates that comparator information for one or both PFDs is not available. <0039> EFI COMP INOP EFI COMP MON EFI COMP MON caution (amber) Indicates that a comparator miscompare has been detected. <0006> Primary Page Comparator Warnings (amber) Indicate that a comparator miscompare has been detected. <0015> Primary Flight Display Pilot s and Copilot s Instrument Panels EFI Abnormal Indications <MT> Figure

17 Electronic Flight Instrument ystem Vol C. Comparator Function A comparison of displayed data is performed by each PFD to ensure that the same data is shown on both PFDs. Comparison of roll, pitch, heading, altitude and airspeed information is performed continuously. Comparison for radio altitude, flight director pitch, IL localizer and IL glide slope are performed during precision landing. When a miscompare condition is detected, the miscompare indicator on both PFDs will flash amber for 5 seconds then come on steady, as long as the miscompare exists. An EFI COMP MON caution message is also displayed on the EICA primary page. D. ystem Circuit Breakers YTEM UB -YTEM CB NAME BU BAR CB PANEL Electronic Flight Instruments t Pilot s Flight Instruments Control Panel PFD 1 MFD 1 EFI CONT PNL 1 Copilot s Flight PFD 2 Instruments MFD 2 Control Panel EFI CONT PNL 2 DC E 4 DC BU 2 2 CB LOCATION D10 D11 C9 K1 K2 K3 NOTE

18 Electronic Flight Instrument ystem Vol THI PAGE INTENTIONALLY LEFT BLANK

19 Air Data ystem Vol AIR DATA YTEM Two air data computers (ADC 1 and ADC 2) provide the primary flight displays (PFD) with air data consisting of airspeed, altitude and vertical speed. The ADCs also provide computed air data (speed, altitude and temperature data) to various aircraft avionics systems. The ADCs convert pitot and static air pressure to electrical signals. The ADCs use static pressure to produce the altitude data and combine static and pitot pressure to produce the airspeed data. Resistance changes from a total air temperature (TAT) probe provide the ADCs with temperature data. The system is controlled by the air data reference panels and has warning and alert capabilities integrated with the EICA. elected speeds and altitude are set using the flight control panel (refer to Chapter 3). A. Pitot tatic ystem The pitot static system supplies pitot and static air pressures to the ADCs, the standby altitude/attitude/airspeed indicator and the cabin pressure control panel (CPCP). The system consists of two pitot/static probes, an alternate pitot probe, alternate static ports and a total air temperature probe (TAT). The pitot static system supplies pitot and static air pressures to the ADCs, the integrated standby instrument (II) and the cabin pressure control panel (CPCP). The system consists of two pitot/static probes, an alternate pitot probe, alternate static ports and a total air temperature probe (TAT).<0083> The pilots and copilots pitot static probes each consist of a pitot mast (P1 and P2) and two static ports (1 and 2). Pitot pressure from each probe is supplied to the same side ADC. tatic pressure from each probe is supplied to each ADC. The alternate pitot probe (P3) supplies pressure inputs to the standby altitude/attitude/airspeed indicator. The alternate pitot probe (P3) supplies pressure inputs to the integrated standby instrument (II).<0083> Electric heating elements protect the pitot-static and TAT probes from icing (refer to Chapter 15, Ice and Rain Protection). NOTE TAT probe readings are inaccurate when the aircraft is on the ground, due to probe heating to protect it from icing. TAT probe readings cannot be used to obtain the ambient static temperature before take-off. Two Mach transducers supply primary Mach compensation data to the stall protection computer. The transducers are connected to the left and right pitot static system and provide a means of isolating a leaky transducer from the rest of the pitot static system. via the static source selectors. The selectors are controlled by mechanical selectors on the pilot s and copilot s side consoles.

20 Air Data ystem Vol ALTERNATE TATIC PORT ALTERNATE PITOT TUBE LEFT PITOT--TATIC PROBE RIGHT PITOT--TATIC PROBE ALTERNATE TATIC PORT TOTAL AIR TEMPERATURE PROBE Pitot tatic ystem --- General Figure

21 Air Data ystem Vol B. Air Data The air data system provides computed air data (speed, altitude and temperature) information to the following systems: Integrated avionics preocessor system (IAP) Attitude and heading reference system (AHR) Inertial reference system (IR) <0025> tall protection computer and flap ECU Air traffic control transponders and TCA Flight control computers and flight director Electronic flight instrument system (EFI) and engine indication and crew alerting system (EICA) displays. The air data system provides the following air data parameters: Pressure altitude and barometric--corrected altitude Vertical speed, indicated airspeed, Mach number and true airspeed (TA) IA reference (automatically through the AP control or manually through the air data reference panel) tatic air temperature (AT) Calibrated and indicated airspeed (CA / IA) Overspeed warning (present airspeed and Vmo) Total air temperature (TAT) Temperature variations from international standard atmosphere (IA). In addition to the above parameters, the air data system computes and controls the following reference values and parameters: Preselect altitude Airspeed trend vector Maximum allowable speed (V MO ) Maximum allowable Mach (M MO ) Vertical speed references.

22 Air Data ystem Vol C. Air Data Reference Panels The air data reference panels (ARP) are located on the pilot s and copilot s side panels. Each ARP is used to enable selection of airspeed reference pointers and barometric correction for altitude. Each ARP functions with the same-side ADC, display control panel, primary flight display and multifunctional display. The ARP is divided into three sections: The speed references section is used to select and input changes to the various target and speed settings (V1, VR, V2 and VT). Both PFDs will display the same values. The altitude references section is used to set minimum descent altitude (MDA) and decision height (DH) values and to initiate radio altimeter self test. The barometric references section is used to select and input changes to the ADC barometric pressure, to select indicating units (hpa or inhg) and to set standard barometric pressure. Each PFD can have a different barometric pressure setting. The last value selected is retained in the ADC memory for the next power up.

23 Air Data ystem Vol PILOT AIR DATA REFERENCE PANEL FLIGHT CONTROL PANEL COPILOT AIR DATA REFERENCE PANEL AIR TRAFFIC CONTROL TRANPONDER 1 AIR TRAFFIC CONTROL TRANPONDER 2 PITOT ATTITUDE/ ACCELERATION ATTITUDE/ ACCELERATION PITOT TATIC TOTAL AIR TEMPERATURE AIR DATA COMPUTER 1 INTEGRATED AVIONIC PROCEOR YTEM HEAD--UP GUIDANCE YTEM AIR DATA COMPUTER 2 TATIC TOTAL AIR TEMPERATURE <0026> ATTITUDE AND HEADING AHR 1 / IR 1 <0025> ALTITUDE; MACH/AIRPEED; VERTICAL PEED (AHR ONLY). ATTITUDE AND HEADING AHR 2 / IR 2 <0025> PFD 1 MFD 1 MFD 2 PFD 2 Air Data ystem <MT> Figure

24 Air Data ystem Vol Mach Transducer 1 (Pilot s ide) tandby Mach Transducer 2 (Copilot s ide) (Mach data to P Channel 1) Instrument (Mach Data to P Channel 2) Pilot s Mach Transducer ource elector / Isolation Valve Copilot s Mach Transducer ource elector / Isolation Valve MACH TRAN 1 MACH TRANDUCER PITOT MACH TRANDUCER TATIC MACH TRANDUCER PITOT ELECTOR VALVE CLOED MACH TRANDUCER TATIC ELECTOR VALVE CLOED MACH TRAN 2 ELECTOR VALVE CLOED ELECTOR VALVE CLOED Water Drains Pitot tatic ystem Figure

25 Air Data ystem Vol DH / MDA Used to select decision height or minimum descent altitude. DH -- Decision height readout is selected to be adjusted. MDA -- Minimum descent altitude readout is selected to be adjusted. EL Used to alternately select V1, VR or V2 to the edit field when VPD is selected. TGT EL PEED REF VPD PUH / ET / OFF Used to adjust selected altitude readout. When pushed, the selected altitude readout (DH or MDA) is displayed on the PFD. When rotated, the selected altitude readout is adjusted (DH in 1--ft. increments, MDA in 10--ft. increments). When pushed again, the selected altitude readout is removed. DH RA TET MDA RA TET Used to initiate radio altitude test. HPA / IN BARO HPA / IN Used to alternately select the barometric pressure to be displayed in hectopascals or inches of mercury. TGT / VPD Used to select target or V speeds. TGT -- VT speed is selected to be displayed on the edit field. VPD -- V1, VR and V2 speeds are selected to be displayed on the edit field. Alternate selection of V1, VR and V2 is made using EL. Air Data Reference Panel Pilot s and Copilot s ide Panels PUH / ET / OFF Used to adjusts the selected speed readout displayed on the edit field. When pushed, the selected speed readout is displayed. When rotated, the selected speed readout is adjusted. When pushed again, the selected speed readout is removed. BARO Used to adjust barometric pressure. When pushed, the barometric pressure is set to the standard value of inhg or 1013 hpa. When rotated, the barometric pressure setting is adjusted. Air Data Reference Control Panel Figure

26 Air Data ystem Vol Mach Readout (white) Indicates Mach speed. Displayed when Mach is above 0.45 and is removed when Mach is below Airspeed Indicator IA /Mach Reference (magenta) Indicates airspeed as selected using the speed knob on flight control panel. peed Reference (cyan) Indicates reference speed as set by pilot using the speed reference knob on air data reference panel. Overspeed Cue (red/black checkerboard) Assends from Vmo/Mmo to top of tape window to indicate maximum speed allowable. If speed is more than 3 kts greater than Vmo or equivalent Mmo, overspeed clacker sounds. Warning continues until speed is 3 kts below Vmo/Mmo. CLACKER TONE Indicated Airspeed Tape (white) Moving tape that indicates current airspeed. Tape range is 40 to 400 knots with a display of 80 knots. Marks at 5 knot increments. Digits at 20 knot increments. IA Bug (magenta) Indicates airspeed reference marker as set by pilot using the speed knob on flight control panel. tall peed Indicator (green line) Indicates 1.25 times the computed stall speed. Displayed in flight only. <FAA> Low peed Cue (red/black checkerboard) Descends from stick shaker speed to edge of tape window and acts as cue to impending stall speed. Displayed 3 seconds after lift--off. Airspeed Indicator If AOA data fails, checkerboard stops at 100 kts. and is replaced by a yellow line up to 120 kts. Indicated Airspeed and Mach Indications <MT> Figure Primary Flight Display Pilot s and Copilot s Instrument Panels T 2 R 1 AP <0015> Trend Vector (magenta) Indicates predicated airspeed within next 10 seconds. Indicated Airspeed Pointer (white) Indicates current airspeed. peed Reference Bugs (cyan) Removed 7.5 seconds after speed is exceeded (except target speed). 1 Takeoff decision speed (V1) R Rotate airspeed (VR) 2 Take--off safety speed (V2) T Target speed (VT)

27 Air Data ystem Vol BRT IA Flag (red) Indicates that airspeed data has failed. Appears in place of airspeed tape IA FT IN V2 142 FM CR W NM YUL 0.0 ADF1 ADF2 TO TO N <0015> 80 Primary Flight Display Pilot s and Copilot s Instrument Panels VT 170 V2 142 VR 136 V1 131 peed Reference Table (cyan) Displayed on ground only. Indicates reference speeds as set using speed reference knob on the air data reference panel. Airspeed Indicator Indicated Airspeed Flag --- Primary Flight Director <MT> Figure

28 Air Data ystem Vol Preselected Altitude Readout (magenta) Indicates preselected altitude to nearest 100 feet, as set using altitude knob on flight control panel. Metric Preselected Altitude Readout (magenta) Indicates preselected altitude in meters. Displayed when metric altimeter is selected on. Altitude Indicator Barometric Pressure etting Readout (cyan) Indicates selected barometric pressure expressed in inches of mercury or hectopascals, as set using barometric knob and on air data reference panel. <0023> Barometric pressure setting readout flashes when: Airplane climbs through 17,800 ft and barometric pressure setting is not set to standard value. Airplane descends through 18,500 ft and barometric pressure setting is set to standard value. Metric Altitude Readout (white) Indicates airplane altitude in meters. Displayed when metric altimeter is selected on. <0029> AP METRIC ALT ON OFF METRIC ALT ON -- Metric altitude readout and metric preselected altitude readout are displayed on PFDs. OFF -- Metric altitude readout and metric preselected altitude readout go out. <0015> Preselect Altitude Bug (magenta) Lines at coarse and fine tape indicate preselected altitude as set using altitude knob on flight control panel. Altitude Readout (white) Indicates airplane barometric altitude. Metric Altimeter witch Center Pedestal Altitude Indicator Barometric Altitude Tape (white) Moving tape with fixed window (digital readout) that indicates barometric altitude from --1,000 to 50,000 feet with a display of 450 feet. Fine Tape Marks at 20 foot increments. Digits at 100 foot increments. Coarse Tape mall rectangles at 500 foot increments. Large rectangles at 1000 foot increments. Altitude Indications <MT> Figure

29 Air Data ystem Vol D. Altitude Alerts The altitude alert system alerts the flight crew that a preselected altitude has been reached or a deviation from a preselected altitude has occurred. When the aircraft is cleared to change altitude, the preselected altitude is set on the PFD through the flight control panel (FCP). There are three types of alerts that can occur: Acquisition mode Cross side tracking Deviation mode. Pending Rectification NOTE An anomaly has been discovered in the ADC software which causes the aural altitude alerter (C--Chord) not to cancel if an AFC transfer is made while the aural alert relay is energized. If the altitude alerter does not cancel automatically after 1 second because the AFC transfer was operated while the aural alert relay was energized, briefly switch the AFC transfer back to the previous setting. Once the aural altitude alerter cancels the AFC transfer may be reselected as required.

30 Air Data ystem Vol Altitude Flag (red) Indicates altitude data has failed. Appears in place of altitude tape <0015> Negative Altitude Flag (yellow) Appears at altitudes less than 0 feet. N E G Altitude Indicator Altitude Alerts <MT> Figure

31 Air Data ystem Vol E. Acquisition Mode Altitude alerts are inhibited in approach mode, when glideslope is captured and there are valid autopilot steering commands. The ADC will set a one second acquisition alert warning (altitude C-cord warning aural) and flash the preselected altitude readout when the present altitude is within ±1,000 feet of capturing the preselected altitude. The readout will stop flashing when the altitude is within ±200 feet of the preselected altitude. The alert can be cancelled by pressing the altitude knob on the flight control panel. F. Cross ide Tracking Each ADC compares the preselect altitude value from both computers for equality. If the values are not equal, the preselect altitude digits on the display change from magenta to cyan. G. Deviation Mode After the preselected altitude is captured, if the altitude deviates from the preselected altitude by more than ±200 feet, a deviation alert warning (aural C chord) will be set and the preselected altitude readout and bug will change from magenta to amber and begin to flash. The readout and bug will return to normal once the altitude is back within deviation limits. A deviation alert will also be made if the airplane has gone within the acquisition limits on an altitude capture but then deviates by more than 100 feet from the preselected altitude. H. Air Data Reversion Normally, each ADC provides data to the same side PFD. If one ADC should fail, the other computer may be used to supply data to both PFDs. This is done by selecting the AIR DATA knob, to the 1 or 2 position, on the ource elector Panel.

32 Air Data ystem Vol Minimum Descent Altitude Readout (cyan) Indicates MDA as set on the air data reference panel. Minimum Descent Altitude Alert (amber) Indicates that airplane has arrived at minimum descent altitude. Minimum Descent Altitude Pointer (cyan) Indicates MDA, as set on the air data reference panel. Disappears when out of range. Flashes during MDA alert. <0015> Minimum Descent Altitude Indications <MT> Figure

33 Air Data ystem Vol Vertical peed cale (white) Non--linear scale of vertical speed between 4,000 feet per minute. mall ticks at 250 FPM. Large ticks at 500 FPM. Digits at 1,000, 2,000 and 4,000 FPM. Vertical peed Pointer (green) Indicates vertical speed in feet per minute. Vertical peed Readout (green) Indicates current vertical speed from 0 to 15,000 FPM. From 0 to 9,950 FPM, display is at 100 FPM. Above 9,950 FPM, display is at 1,000 FPM. If rate is greater than 10,000 FPM, decimal point disappears. NOTE Vertical speed pointer and readout turn red when a TCA resolution advisory is issued and speed is not within corrective limits (refer to Chapter 18). <0015> Vertical peed Flag (red) Indicates that vertical speed data has failed. Appears in place of vertical speed scale, pointer and readout. Vertical peed Indication and Flag <MT> Figure

34 Air Data ystem Vol AIR DATA NORM -- Each air data computer supplies data to the same side display Air data computer 1 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs Air data computer 2 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs. ource elector Panel Center Pedestal ource elector --- Air Data Panel Figure

35 Air Data ystem Vol <0015> ADC 2 ADC 1 or 2 (amber) Indicates that single air data computer source has been selected. ADC 1 -- Air data computer 1 selected. ADC 2 -- Air data computer 2 selected. Air Data Flags --- Primary Flight Display <MT> Figure

36 Air Data ystem Vol I. ystem Circuit Breakers YTEM UB -YTEM CB NAME BU BAR CB PANEL Flight Data CB LOCATION Air Data ADC 1 DC E 4 D3 Computer ADC TBY DC BAT 1 P8 ADC 2 DC BU 2 2 H6 NOTE

37 Radio Altimeter ystem Vol RADIO ALTIMETER YTEM The radio altimeter (RADALT) system provides an accurate measurement of absolute altitude (height above terrain) from 0 to 2500 feet AGL. Radio altitude information is supplied to the following: There are two radio altimeter (RADALT) systems installed on the aircraft. Each system provides an accurate measurement of absolute altitude (height above terrain) from 0 to 2500 feet AGL. Radio altitude information is supplied from both radio altimeters to the following: <0045> PFD s Flight control systems Ground proximity warning system (GPW) Enhanced ground proximity warning system (EGPW) <0040> Traffic alert and collision avoidance (TCA). The radio altimeter provides the pilot s and copilot s PFDs with the following: Radio altitude readout Decision height readout Decision height alerts and radio altimeter fail flags. When a failure is detected during flight, a red warning flag is displayed on the PFD s. The radio altitude display is displayed as both a digital and a moving tape readout. The digital readout appears as the aircraft descends through 2,500 feet. The tape is an analog scale that is displayed when the airplane is below an altitude of 1,225 feet. Decision height is set (from 0 to 999 feet) using either pilot s air data reference panel. A test button is provided on the air data reference panel to verify the operation of the radio altimeter system.

38 Radio Altimeter ystem Vol PFD 1 MFD 1 MFD 2 PFD 2 <0040> <0040> Radio Altimeter ystem <MT> Figure

39 Radio Altimeter ystem Vol DH / MDA Used to select decision height or minimum descent altitude. DH -- Decision height readout is selected to be adjusted. MDA -- Minimum descent altitude readout is selected to be adjusted. PUH / ET / OFF Used to adjust selected altitude readout. When pushed, the selected altitude readout (DH or MDA) is displayed on the PFD. When rotated, the selected altitude readout is adjusted (DH in 1 ft increments, MDA in 10 ft increments). When pushed again, the selected altitude readout is removed. EL DH MDA HPA / IN TGT PEED REF VPD RA TET BARO RA TET Used to initiate radio altitude test. Air Data Reference Panel Pilot s and Copilot s ide Panels Air Data Reference Control Panel Figure

40 Radio Altimeter ystem Vol Decision Height Readout (cyan) Indicates selected decision height as set on the air data reference panel (range is 0 to 999 feet). Red dashes indicate failed input. Radio Altimeter Indicates current radio altitude. Displayed upon descent below 1,225 feet RA. Decision Height Alert (amber) Indicates that airplane has arrived at decision height. During go--around, alert is disabled at decision height +100 feet. Alerts inhibited below 5 feet. DECIION HEIGHT Radio Altitude Readout (green) Indicates radio altitude from 0 to 2,500 feet. At decision height, readout turns amber. Displayed upon descent below 2,500 feet RA. Primary Flight Display Pilot s and Copilot s Instrument Panels Decision Height Pointer (cyan) Indicates selected decision height as set on the air data reference panel. Disappears when out of range. not included in <JAA> Ground Bar (amber) Indicates terrain. Radio Altimeter RA Flag (red) Indicates that radio altitude data has failed. Appears in place of radio altitude readout. <0015> Primary Flight Display Pilot s and Copilot s Instrument Panels Radio Altimeter Indication <MT> Figure

41 Radio Altimeter ystem Vol A. ystem Circuit Breakers YTEM UB -YTEM CB NAME BU BAR CB PANEL Radio Altimeter Altimeter CB LOCATION NOTE RAD ALT 1 DC BU 1 1 K7 RAD ALT 2 DC BU 2 2 L1 <0045>

42 Radio Altimeter ystem Vol THI PAGE INTENTIONALLY LEFT BLANK

43 Attitude and Heading Reference ystem Vol ATTITUDE AND HEADING REFERENCE YTEM The attitude and heading reference system (AHR) is a gyro reference system that generates angular rate and linear acceleration information about the aircraft axis. The AHR is a dual system with two independent attitude and heading computers. Each computer receives corrected heading information from an individual flux detector which sense the earth s magnetic field. Each computer also receives information from the same side air data system. This information, together with accelerometer sensor data, is processed and sent to the integrated avionics processor system which interfaces with the flight control computers and flight management computers. These signals are also routed to the TCA, GPW, weather radar, fuel system, stall protection system, flight data recorder and data concentrator units. These signals are also routed to the TCA, EGPW, weather radar, fuel system, stall protection system, flight data recorder and data concentrator units. <0040> AHR provides attitude and heading information to the electronic flight instruments. The PFD s display AHR alignment flags during initialization (30 to 70 seconds). If aircraft primary power is lost, the AHR will continue to operate on battery bus power for 11 minutes. Attitude is displayed on the attitude direction indicator (ADI) of the primary flight displays and heading is displayed on the horizontal situation indicator (HI) portions of the displays. AHR mode selections are made using the pilot or copilot compass control panel. The AHR normally operates in magnetic (MAG) mode. Directional gyro (DG) mode is intended to operate as a heading reference, only for a short period of time, near areas where magnetic disruptions exist and does not use data from the flux detector. A slew switch is provided to change heading direction. The switch is operational in both MAG and DG modes. In DG mode it is used periodically to correct for drift. In MAG mode, it also causes the heading to slew in the selected direction. When the switch is released in MAG mode, the heading will slowly slave back to the heading defined by the flux detector. 2. INERTIAL REFERENCE YTEM <0025> The inertial reference system (IR) provides inertial outputs of attitude, heading, angular rates, linear acceleration and present position to be displayed on the flight displays and to be used by other avionics systems. The IR is a dual system with two inertial reference units (IRU) and a dual mode select unit (MU). Each IRU receives information from the same side air data system. The IRU measures inertial motion sensed by the inertial instruments and computes attitude and heading data. This information is processed and sent to the integrated avionics processor system which interfaces with the flight control computers and flight management computers. These signals are also routed to the TCA, EGPW, weather radar, fuel system, stall protection system, flight data recorder and data concentrator units. The MU provides pilot selection of the IR modes.

44 Attitude and Heading Reference ystem Vol The IR provides attitude and heading information to the electronic flight instruments. Attitude is displayed on the attitude direction indicator (ADI) of the primary flight displays and heading is displayed on the horizontal situation indicator (HI) portions of the displays. Heading is selected to magnetic or true using the flight management system (refer to Chapter 18). The IR normally operates in navigation mode. In navigation mode, it is not possible to update the IR position, however, it is possible to perform a rapid realignment while on the ground. Attitude mode is a reversionary mode, used when the IRU has detected an inertial failure or inaccuracies of the navigation operation in flight. Attitude mode does not provide position data. In attitude mode, the heading may drift and must be corrected using the flight management system (FM). If the FM is not available, the EICA control panel can be used to make heading corrections. Attitude mode is annunciated on the EICA status page.

45 Attitude and Heading Reference ystem Vol PFD 1 MFD 1 MFD 2 PFD 2 <PRE0025> ATTITUDE HEADING COMPUTER 1 INERTIAL REFERENCE YTEM 1 ATTITUDE HEADING COMPUTER 2 INERTIAL REFERENCE YTEM 2 <0025> <0025> <PRE0025> NAV OFF <PRE0025> ATT OFF NAV ATT <0025> <0025> <PRE0025> 1 IR 2 <0025> <0025> <PRE0025> <PRE0025> DCU 1 & 2 DCU 1, 2 & 3 <0019> HEAD--UP GUIDANCE YTEM <0026> <PRE0025> PITCH/ROLL/HEADING ANGLE PITCH/ROLL/YAW RATE LONG./LAT./NORMAL/CRO HEADING ACCELERATION ALONG HEADING/VERTICAL ACCELERATION ERROR COMPENATION AND FLUX DETECTOR MIALIGNMENT COMPENATOR (COMP) Attitude and Heading Reference ystem/inertial Reference ystem <MT> Figure

46 Attitude and Heading Reference ystem Vol DG/MAG Used to set AHR mode DG -- HI performs like a directional gyro and does not use data from the flux detectors. MAG -- HI is continuously adjusted using data from the flux detectors. DG COMPA + LEW Used to periodically correct heading when in DG mode. Will move reading in MAG mode, but returns to previous heading when switch is released. -- lews HI graphic reading to the right. -- lews HI graphic reading to the left. - <0025> OFF NAV ATT 1-IR -2 Used to select IR mode. OFF -- Removes power from IR. NAV -- IR operates in navigation mode. ATT -- IR operates in attitude mode. OFF NAV ATT MAG LEW Pilot s and Copilot s Compass Control Panel Center Pedestal 1 IR 2 IR Mode elect Unit Center Pedestal Compass Control Panel/Inertial Reference ystem Mode elect Unit <MT> Figure

47 Attitude and Heading Reference ystem Vol Attitude Director Indicator Roll Pointer (white) Indicates roll angle Pointer rotates along fixed roll scale. Primary Flight Display Pilot s and Copilot s Instrument Panels lip / kid Indicator (white) Indicates lateral acceleration. Moves with roll pointer. Lateral displacement from center of roll pointer indicates airplane is slipping or skidding. Roll cale (white) Fixed scale that indicates roll attitude. mall marks at 10 and 20 Large marks at 30 and 60 mall triangle at 45 Horizon Line (white) Indicates roll and pitch attitude relative to airplane symbol. Horizon bar rotates to display roll attitude and moves vertically to display pitch attitude. The boxes at ends of horizon bar represent airplane wing tips Attitude Director Indicator <0015> Airplane ymbol (black) Indicates position of airplane in relation to horizon index. Attitude Director Indications <MT> Figure

48 Attitude and Heading Reference ystem Vol <0015> elected Heading Readout (magenta) Indicates selected heading as set using heading knob on flight control panel. Removed 5 seconds after heading is selected. Horizontal ituation Indicator Primary Flight Display Pilot s and Copilot s Instrument Panels elected Heading Bug (magenta) Indicates selected heading as set using heading knob on flight control panel. When bug is off scale, a dashed line is displayed from center of compass to selected heading. Lubber Line (white) Fixed reference for reading current airplane heading. Fixed index marks are located around compass rose at 45 degree increments. Compass Rose (white) Rotating card indicates airplane current magnetic heading under fixed lubber line. mall marks at 5 degree increments. Larger marks at 10 degree increments. Digits and cardinal points at 30 degree increments. Horizontal ituation Indicator Airplane ymbol (white) Indicates center of compass rose. elected Heading Readout <MT> Figure

49 Attitude and Heading Reference ystem Vol A. Display Reversion Display capability is maintained when sensor data failure occurs. Either PFD (or MFD when in PFD format) can be configured to display data from either attitude and heading reference system by operation of a reversionary switch on the source selector panel. election of alternate data sources is indicated to the flight crew by yellow single source flag on the PFD and MFD. Display capability is maintained when sensor data failure occurs. Either PFD (or MFD when in PFD format) can be configured to display data from either inertial reference system by operation of a reversionary switch on the source selector panel. election of alternate data sources is indicated to the flight crew by yellow single source flag on the PFD and MFD. <0025>

50 Attitude and Heading Reference ystem Vol ATTD HDG Used to revert attitude and heading reference systems. NORM -- Each attitude and heading computer supplies data to the same side display Attitude and heading computer 1 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs Attitude and heading computer 2 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs. ATTD HDG Used to revert inertial reference systems. NORM -- Each inertial reference unit supplies data to the same side display Inertial reference unit 1 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs Inertial reference unit 2 supplies data to both pilot and copilot displays. An amber source message is displayed on both PFDs. <0025> ource elector Panel Center Pedestal ource elector Panel Center Pedestal ource elector Panel <MT> Figure

51 Attitude and Heading Reference ystem Vol <0025> ATT 1 or 2 (amber) Indicates that single inertial reference source has been selected. ATT 1 -- Inertial reference unit 1 selected. ATT 2 -- Inertial reference unit 2 selected Primary Flight Display Pilot s and Copilot s Instrument Panels MAG1,MAG2,DG1orDG2(amber) Indicates heading selection when a single attitude and heading source has been selected. <0025> MAG 1, MAG 2, TRU 1 or TRU 2 (amber) Indicates heading selection when a single Inertial reference source has been selected. <0015> Multifunction Display - HI Mode Pilot s and Copilot s Instrument Panels Attitude and Heading ource election <MT> Figure

52 Attitude and Heading Reference ystem Vol ATT <0015> ATT MAG <0025> ATTFlag(red) Indicates that onside or both attitude and heading systems have failed. ATTFlag(red) Indicates that onside or both inertial reference systems have failed. Primary Flight Display Pilot s and Copilot s Instrument Panels BRT WX UTC 16:13 TA 0 FM 2 CR 243 YUL 13.0 NM TTG G 0 MAG AT 12C TAT 15C <0025> MAG 1 or DG Flag (red) Indicates that onside or both attitude and heading systems are faulty or out of tolerance. MAG or TRU Flag (red) Indicates that onside or both inertial reference systems are faulty or out of tolerance. Multifunction Display - HI Mode Pilot s and Copilot s Instrument Panels Attitude/Heading ource Failure Indications <MT> Figure

53 Attitude and Heading Reference ystem Vol B. Initialization and Alignment AHR initialization and operation occurs automatically when electrical power is established and the aircraft is stationary. Initialization in MAG mode takes about 70 seconds. DG mode requires a much longer time to initialize. In flight, initialization requires straight, unaccelerated level flight. The primary flight displays (PFD s) present a flashing initialization alignment message during initialization. IR initialization takes about 7 minutes at normal temperature. The IR requires that the initial position be entered using the flight management system (FM). The primary flight displays (PFD s) present a flashing initialization alignment message during initialization. Upon successful alignment, the IR will automatically sequence into navigation mode. Attitude alignment takes 1 minute or 34 seconds when switching from navigation to attitude mode, provided the aircraft is stationary on the ground or in straight and level flight. <0025> The magnetic flux detectors used to originate heading information are sensitive to localized magnetic fields and magnetic anomalies. The effects and the procedural responses to these conditions are presented in the Collins AH-85 / 85E Attitude Heading ystem Pilot s Guide.